CN215337998U - Small-caliber rocket bomb - Google Patents

Abstract

The utility model discloses a small-caliber rocket projectile, which comprises a launching engine section, a projectile-mounted computer and a main engine compartment section; the launching engine section is arranged at the tail of the projectile body, a mounting opening is formed in the center of the launching engine section, a laser receiver is arranged in the mounting opening, and a protective cover is detachably connected to the mounting opening; the missile-borne computer is arranged in the middle of the missile body, and is in signal connection with the laser receiver through a signal line; the main engine compartment section is arranged on the projectile body and located between the missile-borne computer and the launching engine section, two ends of the main engine compartment section are respectively fixed with the missile-borne computer and the launching engine section, and a wiring groove is formed in the main engine compartment section and used for containing a signal wire connected with the missile-borne computer and the laser receiver. The laser receiver is arranged in the launching engine section at the tail part of the projectile body, so that the laser receiver does not influence the wiring condition of a power line and a signal line and is convenient to install.

Description

Small-caliber rocket bomb

Technical Field

The utility model relates to the technical field of rocket projectiles, in particular to a small-caliber rocket projectile.

Background

At present, the small-size rocket bomb (40mm bore) that domestic relevant enterprise developed adopts laser to drive and restraints the guidance mostly, locate the middle part of projectile body with laser receiver usually, but because the space at projectile body middle part is narrow and small and be equipped with the required signal line of guidance control, the power cord, consequently, make the inner structure of projectile body compacter, can influence the power cord with the middle part of laser receiver projectile body, the wiring condition of signal line, and the installation of the laser receiver of not being convenient for, when the rocket popped out the thorax simultaneously, the laser receiver who sets up at projectile body middle part still can receive the influence that the thorax pressed, easy emergence damages.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a small-caliber rocket projectile to solve the problems of the background technology.

The technical scheme of the utility model is as follows: a small-caliber rocket projectile comprises a launching engine section, a projectile-borne computer and a main engine compartment section; the launching engine section is arranged at the tail of the projectile body, a mounting opening is formed in the center of the launching engine section, a laser receiver is arranged in the mounting opening, and a protective cover is detachably connected to the mounting opening; the missile-borne computer is arranged in the middle of the missile body and is in signal connection with the laser receiver through a signal line; the main engine compartment section is arranged on the projectile body and located between the missile-borne computer and the launching engine section, two ends of the main engine compartment section are respectively fixed with the missile-borne computer and the launching engine section, and a wiring groove is formed in the main engine compartment section and used for containing a signal wire connected with the missile-borne computer and the laser receiver.

Preferably, a plurality of first clamping grooves are formed in the side wall, close to the rear end of the transmitter section, of the mounting port, a first mounting hole is formed in each first clamping groove and is formed in the length direction of the transmitter section, an axial elastic pin is arranged in each first mounting hole, a plurality of clamping plates matched with the first clamping grooves are fixed on the outer side wall of the protective cover, each clamping plate is correspondingly clamped in each first clamping groove, a second clamping groove is formed in the rear end of each clamping plate, a second mounting hole is formed in the groove wall, opposite to the center of the transmitter section, of each first clamping groove, a radial elastic pin is arranged in each second mounting hole, and one end of each radial elastic pin is clamped in each second clamping groove and can move in each second clamping groove.

Preferably, the front end of the main engine room section is fixedly connected to the missile-borne computer through screws, the rear end of the main engine room section is provided with a plurality of grooves, the front end of the launch engine section is provided with a plurality of protrusions matched with the grooves, and the rear end of the main engine room section is in concave-convex combination connection with the front end of the launch engine section and is fixed through screws.

Preferably, the middle part of the main engine compartment section is the minimum part of the overall diameter of the rocket projectile, the middle part of the main engine compartment section is provided with an arc wing rolling mechanism, and the arc wing rolling mechanism is attached to the circumference of the middle part of the main engine compartment section in a contraction state.

Preferably, the front end of the missile-borne computer is provided with a battle cabin section, the rear end of the battle cabin section is connected with the front end of the missile-borne computer in a matched mode through a rabbet, the circumferential surface of the joint of each rabbet is fixedly connected through a plurality of screws, and the battle cabin section comprises a battle assembly and a fuse assembly.

Preferably, the front end of the cabin section of the warhead is provided with a battery cabin section, a thermal battery is arranged in the battery cabin section, the thermal battery is electrically connected with the missile-borne computer and the laser receiver respectively, the rear end of the battery cabin section is connected with the front end of the cabin section of the warhead in a matched mode through a seam allowance, and the circumferential surface of the joint of the seam allowances is fixedly connected through a plurality of screws.

Preferably, the front end of the battery cabin section is provided with a steering engine cabin section, the rear end of the steering engine cabin section is connected with the front end of the battery cabin section through a seam allowance in a matched manner, and the circumferential surface of the joint of the seam allowances is fixedly connected through a plurality of screws.

Preferably, the steering engine cabin section is a single steering engine cabin section, the steering engine cabin section comprises a steering engine cabin section shell, a steering engine, two fixed rudder pieces and two movable rudder pieces, the two fixed rudder pieces are horizontally fixed on two sides of the steering engine cabin section shell respectively, the steering engine is arranged inside the steering engine cabin section shell, the steering engine is electrically connected with the missile-borne computer and the thermal battery respectively, and the two movable rudder pieces are fixedly connected with two ends of a steering engine shaft of the steering engine respectively.

Compared with the prior art, the utility model has the beneficial effects that:

1. the laser receiver is arranged in the launching engine section at the tail part of the projectile body, so that the laser receiver does not influence the wiring condition of a power line and a signal line and is convenient to install; the laser receiver is arranged in the transmitting engine section instead of being exposed in the middle of the projectile body, so that the laser receiver can be protected from being influenced by excessive chamber pressure by the cooperation of the transmitting engine section and the protective cover; meanwhile, a wiring groove is formed in the main engine compartment section, and a signal line connected with the missile-borne computer and the laser receiver is stored through the wiring groove, so that the missile body is more compact in structure and convenient to launch.

2. The protective cover can reduce the influence of smoke generated when the transmitting engine section is ignited on the signal receiving of the laser receiver, and meanwhile, the protective cover can easily and quickly fall off after the rocket projectile is launched under the matching of the radial elastic pin and the axial elastic pin, so that the protective cover has strong practicability.

3. According to the rocket projectile control device, the flight of the rocket projectile is adjusted and controlled through the single-channel steering engine, the single electric steering engine is used for controlling the group of ducks to follow up in the whole process, the control flight of the rotating rocket projectile is realized, the control mode is simple, the stability is high, and in addition, the cost is low compared with that of a multi-channel steering engine.

4. The cabin sections are matched and positioned through the seam allowances and are fixed in a screw connection mode, so that the parts have certain interchangeability and can be adjusted appropriately and flexibly to change the position of the mass center of the parts.

Drawings

FIG. 1 is a schematic front view of the present invention;

FIG. 2 is a schematic structural view of the present invention;

FIG. 3 is a rear view of the present invention;

FIG. 4 is an enlarged view of a portion of FIG. 3 according to the present invention;

FIG. 5 is a schematic view of the present invention in a winged arc installation position;

FIG. 6 is a front view of a main engine compartment section of the present invention;

fig. 7 is a front view of the transmitter engine section of the present invention.

Detailed Description

The following describes in detail an embodiment of the present invention with reference to fig. 1 to 7. In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.

The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature; in the description of the present invention, "a plurality" means two or more unless otherwise specified.

Examples

As shown in fig. 1 and 2, a small caliber rocket projectile includes a launch engine section 7, a payload computer 4, and a main engine compartment section 5; the launching engine section 7 is arranged at the tail of the projectile body, a mounting opening 70 is formed in the center of the launching engine section 7, a laser receiver 8 is arranged in the mounting opening 70, and a protective cover 9 is detachably connected to the mounting opening 70; the missile-borne computer 4 is arranged in the middle of the missile body, and the missile-borne computer 4 is in signal connection with the laser receiver 8 through a signal line; the main engine compartment section 5 is arranged on the projectile body and located between the missile-borne computer 4 and the launching engine section 7, two ends of the main engine compartment section 5 are respectively fixed with the missile-borne computer 4 and the launching engine section 7, and a wiring groove is formed in the main engine compartment section 5 and used for containing a signal line connected with the missile-borne computer 4 and the laser receiver 8.

The main engine compartment section 5 and the launching engine section 7 both adopt multi-nozzle solid rocket engines, the launching engine section 7 is designed with corresponding inclination angles, the rocket can be guaranteed to have an initial rotating speed not lower than 20r/s after being ejected out of a chamber, the protective cover 9 can reduce the influence of smoke generated when the launching engine section 7 is ignited on the laser receiver 8 to receive signals, and the protective cover 9 is detachably connected with the mounting port 70, so that the protective cover 9 falls off after being launched to facilitate the laser receiver 8 to receive signals.

Further, as shown in fig. 2 to 4, in order to facilitate the protective cover 9 to fall off after being launched, a plurality of first locking grooves 71 are provided on a side wall of the mounting port 70 near the rear end of the launch motor section 7, a first mounting hole 73 is provided in each first locking groove 71 and arranged along the length direction of the launch motor section 7, an axial elastic pin 94 is provided in each first mounting hole 73, a plurality of locking plates 91 adapted to the first locking grooves 71 are fixed on an outer side wall of the protective cover 9, each locking plate 91 is correspondingly locked in each first locking groove 71, a second locking groove 92 is provided at the rear end of each locking plate 91, a second mounting hole 72 is provided on a groove wall of each first locking groove 71 facing the center of the launch motor section 7, a radial elastic pin 93 is provided in each second mounting hole 72, and one end of the radial elastic pin 93 is locked in the second locking groove 92 and can move in the second locking groove 92. After the rocket projectile is launched out of the chamber, the radial spring pin 93 retracts into the second mounting hole 72 under the action of centrifugal force along with the increase of the rotating speed of the rocket projectile, and meanwhile, the protective cover 9 falls off under the action of the axial spring pin 94.

Further, as shown in fig. 1, 6 and 7, the front end 51 of the main engine room section 5 is fixedly connected to the missile-borne computer 4 through screws, the rear end 53 of the main engine room section 5 is provided with a plurality of grooves 55, the front end of the launcher engine section 7 is provided with a plurality of protrusions 74 matched with the grooves 55, and the rear end 53 of the main engine room section is connected with the front end of the launcher engine section 7 in a concave-convex combination manner and is fixed through screws.

Further, as shown in fig. 1, 2 and 5, a curved wing rolling mechanism 6 is provided in the middle portion 52 of the main engine compartment 5, and in order to contract the curved wing rolling mechanism 6 when the rocket is launched to facilitate launching, the middle portion 52 of the main engine compartment 5 is the smallest part of the overall diameter of the rocket, and the curved wing rolling mechanism 6 is attached to the circumference of the middle portion 52 of the main engine compartment 5 in a contracted state to facilitate the rocket to be ejected out of the chamber.

Further, as shown in fig. 1 and 2, in order to increase the killing power of rocket projectiles, a warhead cabin section 3 is arranged at the front end of the missile-borne computer 4, the rear end of the warhead cabin section 3 is connected with the front end of the missile-borne computer 4 through a rabbet in a matching manner, the circumferential surface of each rabbet joint is fixedly connected through a plurality of screws, the warhead cabin section 3 comprises a warhead component 31 and a fuze component 32, the warhead component 31 can be a warhead with various types such as armor piercing, explosion and detonation, the killing radius can reach more than 12m, and the warhead can easily destroy soft armor targets, hangars, radars, commanders, live strength and the like of enemies.

Further, as shown in fig. 1 and 2, in order to provide energy required by a control system for the whole rocket projectile, a battery cabin section 2 is arranged at the front end of a battle section 3, a thermal battery is arranged in the battery cabin section 2, the thermal battery is electrically connected with a projectile-mounted computer 4 and a laser receiver 8 respectively, the rear end of the battery cabin section 2 is connected with the front end of the battle section 3 through a rabbet in a matching manner, and the circumferential surface of each rabbet joint is fixedly connected through a plurality of screws. Wherein, the thermal battery provides the required energy of control system for whole rocket projectile, and the thermal battery activates in the launching tube before the transmission.

Further, as shown in fig. 1 and 2, in order to control the flight of the rocket projectile conveniently, a steering engine cabin section 1 is arranged at the front end of the battery cabin section 2, the rear end of the steering engine cabin section 1 is connected with the front end of the battery cabin section 2 through a seam allowance in a matching manner, and the circumferential surface of the joint of the seam allowances is fixedly connected through a plurality of screws.

Furthermore, as shown in fig. 1 and 2, for convenience of control and cost reduction, the steering engine cabin section 1 is a single steering engine cabin section, the steering engine cabin section 1 includes a steering engine cabin section shell 11, a steering engine 12, two fixed rudder pieces 13 and two movable rudder pieces 14, the two fixed rudder pieces 13 are horizontally fixed on two sides of the steering engine cabin section shell 11 respectively, the steering engine 12 is arranged inside the steering engine cabin section shell 11, the steering engine 12 is a double-shaft steering engine, and the two movable rudder pieces 14 are fixedly connected with two ends of a steering engine shaft 15 of the steering engine 12 respectively. The flight condition of the rocket projectile is controlled through the command output by the steering engine 12.

The laser steering device adopts laser beam steering guidance, has the characteristics of low cost, small volume, light weight, long range, high precision and easy operation, has good hitting effect on high-value military targets such as armored vehicles, radars and the like, and uses a single electric steering engine to control a group of ducks and rudders to follow up in the whole process, thereby realizing the control flight of the rotating rocket projectile. The controlled flight process of the rocket projectile is as follows: target locking-rocket projectile loading (safety release) -rocket projectile power-on-projectile-rocket projectile initialization-initial aiming-launching and spinning out of a cylinder-rolling arc wing unfolding-main engine ignition-control system working-target attack; when a soldier finds a target, laser irradiation is utilized to provide a guide beam for a rocket projectile, a shooter launches the rocket projectile, the rocket projectile launches a barrel, a cambered wing mechanism 6 at the tail part of the rocket projectile after launching the barrel is opened, a flying engine is ignited after the rocket projectile launches about 6 meters out of the barrel and enters a laser information field, a laser receiver 8 receives information of the laser information field and calculates a coordinate position (an instruction value) in the laser information field, an missile-borne computer 4 controls a steering engine 12 to correct the deviation in the high-low direction and the azimuth direction according to the instruction value, the rocket projectile is controlled to fly at the center of the laser information field all the time, a ground guidance instrument changes the size of a light spot according to a matched zooming program to ensure that the size of the light spot at the position where the rocket projectile flies is relatively unchanged, and controls a steering engine shaft 15 of the steering engine 12 to drive a movable steering engine 14 to perform pitching and yawing motions to adjust the flying attitude of the rocket projectile, and controlling the rocket projectile to fly along the aiming line until the target is hit.

Although the preferred embodiments of the present invention have been disclosed, the embodiments of the present invention are not limited thereto, and any variations that can be made by those skilled in the art are intended to fall within the scope of the present invention.

Claims (8)

1. A small caliber rocket projectile characterized by comprising:

the projectile body is provided with a launching engine section (7) which is arranged at the tail of the projectile body, a mounting opening (70) is formed in the center of the launching engine section (7), a laser receiver (8) is arranged in the mounting opening (70), and a protective cover (9) is detachably connected to the mounting opening (70);

the missile-borne computer (4) is arranged in the middle of the missile body, and the missile-borne computer (4) is in signal connection with the laser receiver (8) through a signal line;

the main engine compartment section (5) is arranged on the projectile body and located between the missile-borne computer (4) and the launching engine section (7), two ends of the main engine compartment section (5) are fixed with the missile-borne computer (4) and the launching engine section (7) respectively, and a wiring groove is formed in the main engine compartment section (5) and used for accommodating a signal line connected with the missile-borne computer (4) and the laser receiver (8).

2. The small-caliber rocket projectile as claimed in claim 1, wherein a plurality of first slots (71) are formed in the side wall of the mounting port (70) near the rear end of the launching motor section (7), a first mounting hole (73) is formed in each first slot (71) along the length direction of the launching motor section (7), an axial elastic pin (94) is formed in each first mounting hole (73), a plurality of clamping plates (91) matched with the first slots (71) are fixed on the outer side wall of the protective cover (9), each clamping plate (91) is correspondingly clamped in each first slot (71), a second slot (92) is formed in the rear end of each clamping plate (91), a second mounting hole (72) is formed in the slot wall of each first slot (71) facing the center of the launching motor section (7), and a radial elastic pin (93) is formed in each second mounting hole (72), one end of the radial elastic pin (93) is clamped in the second clamping groove (92) and can move in the second clamping groove (92).

3. A small-caliber rocket projectile according to claim 1, wherein the front end (51) of the main engine compartment section (5) is fixedly connected to the missile loader computer (4) through screws, the rear end (53) of the main engine compartment section (5) is provided with a plurality of grooves (55), the front end of the launcher section (7) is provided with a plurality of protrusions (74) matched with the grooves (55), and the rear end (53) of the main engine compartment section is connected with the front end of the launcher section (7) in a concave-convex combination mode and is fixed through screws.

4. A small-caliber rocket projectile according to claim 1, wherein the middle part (52) of the main engine compartment section (5) is the smallest part of the overall diameter of the rocket projectile, the middle part (52) of the main engine compartment section (5) is provided with a rolling wing mechanism (6), and the rolling wing mechanism (6) is attached to the circumference of the middle part (52) of the main engine compartment section (5) in a contracted state.

5. The small-caliber rocket projectile as claimed in claim 1, wherein the front end of the missile-borne computer (4) is provided with a combat section (3), the rear end of the combat section (3) is connected with the front end of the missile-borne computer (4) in a matching way through a rabbet, the circumferential surface of each rabbet joint is fixedly connected through a plurality of screws, and the combat section (3) comprises a combat assembly (31) and a fuze assembly (32).

6. The small-caliber rocket projectile as claimed in claim 5, wherein the front end of the warhead cabin section (3) is provided with a battery cabin section (2), the battery cabin section (2) is internally provided with a thermal battery, the thermal battery is respectively and electrically connected with the missile-borne computer (4) and the laser receiver (8), the rear end of the battery cabin section (2) is in fit connection with the front end of the warhead cabin section (3) through a rabbet, and the circumferential surface of the rabbet joint is fixedly connected through a plurality of screws.

7. The small-caliber rocket projectile as claimed in claim 6, wherein the front end of the battery compartment section (2) is provided with a steering engine compartment section (1), the rear end of the steering engine compartment section (1) is connected with the front end of the battery compartment section (2) through a seam allowance in a matching manner, and the circumferential surface of the joint of the seam allowances is fixedly connected through a plurality of screws.

8. The small-caliber rocket projectile as claimed in claim 7, wherein the steering engine cabin section (1) is a single steering engine cabin section, the steering engine cabin section (1) comprises a steering engine cabin section shell (11), a steering engine (12), two fixed rudder pieces (13) and two movable rudder pieces (14), the two fixed rudder pieces (13) are horizontally fixed on two sides of the steering engine cabin section shell (11) respectively, the steering engine (12) is arranged inside the steering engine cabin section shell (11), the steering engine (12) is electrically connected with the missile-borne computer (4) and a thermal battery respectively, and the two movable rudder pieces (14) are fixedly connected with two ends of a steering engine shaft (15) of the steering engine (12) respectively.

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